FR3109038B1 - Actuation system for an aircraft engine lubrication pump and associated aircraft - Google Patents

Actuation system for an aircraft engine lubrication pump and associated aircraft Download PDF

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Publication number
FR3109038B1
FR3109038B1 FR2003368A FR2003368A FR3109038B1 FR 3109038 B1 FR3109038 B1 FR 3109038B1 FR 2003368 A FR2003368 A FR 2003368A FR 2003368 A FR2003368 A FR 2003368A FR 3109038 B1 FR3109038 B1 FR 3109038B1
Authority
FR
France
Prior art keywords
stator winding
aircraft
actuation system
lubrication pump
engine lubrication
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Active
Application number
FR2003368A
Other languages
French (fr)
Other versions
FR3109038A1 (en
Inventor
Blois Nicolas Bertrand Georges De
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Safran Aircraft Engines SAS
Original Assignee
Safran Aircraft Engines SAS
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Safran Aircraft Engines SAS filed Critical Safran Aircraft Engines SAS
Priority to FR2003368A priority Critical patent/FR3109038B1/en
Priority to CN202180027006.6A priority patent/CN115380455A/en
Priority to US17/995,332 priority patent/US20230142269A1/en
Priority to EP21720801.6A priority patent/EP4128489A1/en
Priority to PCT/FR2021/050531 priority patent/WO2021198597A1/en
Publication of FR3109038A1 publication Critical patent/FR3109038A1/en
Application granted granted Critical
Publication of FR3109038B1 publication Critical patent/FR3109038B1/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Classifications

    • H—ELECTRICITY
    • H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
    • H02K—DYNAMO-ELECTRIC MACHINES
    • H02K7/00—Arrangements for handling mechanical energy structurally associated with dynamo-electric machines, e.g. structural association with mechanical driving motors or auxiliary dynamo-electric machines
    • H02K7/18—Structural association of electric generators with mechanical driving motors, e.g. with turbines
    • H02K7/1807—Rotary generators
    • H02K7/1823—Rotary generators structurally associated with turbines or similar engines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/06—Arrangements of bearings; Lubricating
    • H—ELECTRICITY
    • H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
    • H02K—DYNAMO-ELECTRIC MACHINES
    • H02K11/00—Structural association of dynamo-electric machines with electric components or with devices for shielding, monitoring or protection
    • H02K11/20—Structural association of dynamo-electric machines with electric components or with devices for shielding, monitoring or protection for measuring, monitoring, testing, protecting or switching
    • H02K11/21—Devices for sensing speed or position, or actuated thereby
    • H—ELECTRICITY
    • H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
    • H02K—DYNAMO-ELECTRIC MACHINES
    • H02K7/00—Arrangements for handling mechanical energy structurally associated with dynamo-electric machines, e.g. structural association with mechanical driving motors or auxiliary dynamo-electric machines
    • H02K7/20—Structural association with auxiliary dynamo-electric machines, e.g. with electric starter motors or exciters
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • F05D2220/323—Application in turbines in gas turbines for aircraft propulsion, e.g. jet engines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/70—Application in combination with
    • F05D2220/76—Application in combination with an electrical generator

Landscapes

  • Engineering & Computer Science (AREA)
  • Power Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Microelectronics & Electronic Packaging (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Connection Of Motors, Electrical Generators, Mechanical Devices, And The Like (AREA)
  • Electromagnetic Pumps, Or The Like (AREA)

Abstract

L’invention concerne un système d’actionnement (4) comportant : - une machine électrique tournante génératrice (6) comprenant un premier stator (14) comportant au moins un enroulement statorique de sortie (16) ; - une machine électrique tournante motrice (8) comprenant un deuxième rotor (18), destiné à actionner une pompe de lubrification (2), et un deuxième stator (20) comprenant au moins un enroulement statorique d’entrée (22) ; - une matrice d’interrupteurs (11) électriquement reliée à l’au moins un enroulement statorique de sortie et à l’au moins un enroulement statorique d’entrée, pour électriquement les connecter ou déconnecter entre eux en fonction d’un état de la matrice d’interrupteurs ; et - un dispositif de commande (10) configuré pour, en fonction d’un état d’un signal de commande, commander la matrice d’interrupteurs de façon à connecter électriquement ou non entre eux l’au moins un enroulement statorique de sortie et l’au moins un enroulement statorique d’entrée. Figure 1.The invention relates to an actuation system (4) comprising: - a rotating electrical generator machine (6) comprising a first stator (14) comprising at least one output stator winding (16); - a rotating electric motor machine (8) comprising a second rotor (18), intended to actuate a lubrication pump (2), and a second stator (20) comprising at least one input stator winding (22); - a matrix of switches (11) electrically connected to the at least one output stator winding and to the at least one input stator winding, for electrically connecting or disconnecting them according to a state of the switch matrix; and - a control device (10) configured to, as a function of a state of a control signal, control the matrix of switches so as to connect electrically or not to each other the at least one output stator winding and the at least one input stator winding. Figure 1.

FR2003368A 2020-04-03 2020-04-03 Actuation system for an aircraft engine lubrication pump and associated aircraft Active FR3109038B1 (en)

Priority Applications (5)

Application Number Priority Date Filing Date Title
FR2003368A FR3109038B1 (en) 2020-04-03 2020-04-03 Actuation system for an aircraft engine lubrication pump and associated aircraft
CN202180027006.6A CN115380455A (en) 2020-04-03 2021-03-26 Actuating system for an aircraft engine lubrication pump and associated aircraft
US17/995,332 US20230142269A1 (en) 2020-04-03 2021-03-26 Actuation system for an aircraft engine lubrication pump and associated aircraft
EP21720801.6A EP4128489A1 (en) 2020-04-03 2021-03-26 Actuation system for an aircraft engine lubrication pump and associated aircraft
PCT/FR2021/050531 WO2021198597A1 (en) 2020-04-03 2021-03-26 Actuation system for an aircraft engine lubrication pump and associated aircraft

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR2003368A FR3109038B1 (en) 2020-04-03 2020-04-03 Actuation system for an aircraft engine lubrication pump and associated aircraft
FR2003368 2020-04-03

Publications (2)

Publication Number Publication Date
FR3109038A1 FR3109038A1 (en) 2021-10-08
FR3109038B1 true FR3109038B1 (en) 2022-03-11

Family

ID=70804820

Family Applications (1)

Application Number Title Priority Date Filing Date
FR2003368A Active FR3109038B1 (en) 2020-04-03 2020-04-03 Actuation system for an aircraft engine lubrication pump and associated aircraft

Country Status (5)

Country Link
US (1) US20230142269A1 (en)
EP (1) EP4128489A1 (en)
CN (1) CN115380455A (en)
FR (1) FR3109038B1 (en)
WO (1) WO2021198597A1 (en)

Family Cites Families (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6020711A (en) * 1998-03-05 2000-02-01 The United States Of America As Represented By The Secretary Of The Air Force Multiple winding channel, magnetic coupling-alterable reluctance electrical machines and their fault tolerant control
US6791226B1 (en) * 2003-09-10 2004-09-14 Wavecrest Laboratories, Llc Multiphase motor winding topology and control
CN101400536A (en) * 2007-04-24 2009-04-01 三菱电机株式会社 Electric drive system and hybrid drive system
US9657645B2 (en) * 2013-02-25 2017-05-23 Pratt & Whitney Canada Corp. Engine architecture using electric machine
US9318992B2 (en) * 2013-08-22 2016-04-19 Yaskawa America, Inc. Drive circuit for a pre-phase AC motor
GB201407743D0 (en) * 2014-05-02 2014-06-18 Rolls Royce Plc Gas turbine engine fuel system
US10676205B2 (en) * 2016-08-19 2020-06-09 General Electric Company Propulsion engine for an aircraft
US10759545B2 (en) * 2018-06-19 2020-09-01 Raytheon Technologies Corporation Hybrid electric aircraft system with distributed propulsion
US10906657B2 (en) * 2018-06-19 2021-02-02 Raytheon Technologies Corporation Aircraft system with distributed propulsion

Also Published As

Publication number Publication date
US20230142269A1 (en) 2023-05-11
FR3109038A1 (en) 2021-10-08
CN115380455A (en) 2022-11-22
WO2021198597A1 (en) 2021-10-07
EP4128489A1 (en) 2023-02-08

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